Verification and Validation Testing of the Parachute Decelerator System Prior to the First Supersonic Flight Dynamics Test for the Low Density Supersonic Decelerator Program

Gallon, John C.; Witkowski, Allen

doi:10.2514/6.2015-2162

Cited by 6 publications

(2 citation statements)

References 9 publications

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“…Guidotti et al designed, developed, tested, and carried out in-flight qualification of a parachute recovery system in 2012 (8) . Gallon et al did verification and validation testing of the parachute decelerator system prior to the first supersonic flight dynamics test for the low density supersonic decelerator program in 2015 (9) .…”

Section: Introductionmentioning

confidence: 99%

Development and testing of subsonic tandem deceleration system

Samani

Mahyari

2016

Aeronaut. j.

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For many years, deceleration systems developed in an evolutionary fashion. This evolution needed flight test and experimental data. Concurrently, payload became much more expensive and needed to be safer. Today, there are a variety of methods employed to recover airborne bodies such as bio-capsules, reentry satellites, carrier missiles' boosters, reentry satellites, etc. Most of these methods make use of a parachute landing system in which recovery occurs in multiple phases. This paper studies the final phase of the subsonic recovery scenario for which a multi-phase deceleration system has been designed. To observe and evaluate system performance, a test projectile is designed that accelerates the payload to a certain velocity in order to test the recovery system. Finally, theoretical and test results are compared to indicate the appropriate design and reliable deceleration velocity in a space payload recovery.

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Section: Introductionmentioning

confidence: 99%

Development and testing of subsonic tandem deceleration system

Samani

Mahyari

2016

Aeronaut. j.

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“…Ken Heinde et al [7] developed parachute tests for a missile descent system in 1999, G Guidotti et al [8] designed, developed, tested, and carried out in-flight qualification of a Parachute Recovery System in 2012 . John C Gallon et al [9] did verification and validation testing of the parachute decelerator system prior to the first supersonic flight dynamics test for the low density supersonic decelerator program in 2015.…”

Section: Introductionmentioning

confidence: 99%

Designing a Universal Deceleration System for Sounding Rockets Lighter than 100kg by System Engineering Approach

Samani¹

2017

AAOAJ

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For many years deceleration systems are developed in evolutionary fashion. This evolution needed flight test, and experimental data. This research deals with designing a deceleration system for a sounding rocket. It is mainly aimed at designing a universal deceleration system so that the payload touches the land with a safe velocity. To do so, first a deceleration system is designed for a 25kg payload in altitudes of less than 2km.Having considered flight equations for the sounding rocket and parachute, a number of parameters including recovery weight, landing time and velocity and maximum post-deployment acceleration have been computed for sounding rockets lighter than 250kg. Sensitivity analysis of the payload weight and recovery initiation velocity led to designing a universal deceleration system capable of recovering sounding rockets weighing between 25kg and 75kg with a landing velocity between l0 m/sec and 12m/ sec. Base on system engineering approach, universal deceleration subsystem is design for sounding rocket with various mass.

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